System and method for assembling gas turbine rotor using localized inductive heating

Patent metadata

Field	Value
Publication number	US-10920592-B2
Application number	US-201715844065-A
Country	US
Kind code	B2
Filing date	Dec 15, 2017
Priority date	Dec 15, 2017
Publication date	Feb 16, 2021
Grant date	Feb 16, 2021

Abstract

A method of assembling a rotor is provided, in which each rotor disk comprising a connecting element. The method includes: (a) applying heat to a localized region of a first rotor disk of a plurality of rotor disks to selectively deflect a first connecting element of the first rotor disk, wherein the first rotor disk is stationary during heating; (b) installing the first rotor disk onto a rotor stack containing at least one rotor disk; and (c) repeating steps (a) and (b) for each rotor disk of the plurality of rotor disks; and (d) allowing the rotor disks, when stacked, to cool. When cooled, the respective connecting element of each rotor disk that has been selectively deflected contracts into an interference fit with an adjacent rotor disk. A system for selectively heating a localized region of a rotor disk is also provided.

First claim

What is claimed is:

1. A method of assembling a rotor comprising a plurality of rotor disks, each rotor disk of the plurality of rotor disks comprising a connecting element, the method comprising:
(a) applying heat to a localized region of a first rotor disk of the plurality of rotor disks to selectively deflect a first connecting element of the first rotor disk, wherein the first rotor disk is stationary during the applying of heat; wherein the applying heat to a localized region includes inductive heating using an inductive heating fixture temporarily attached in a stationary position to the rotor disk during the step of applying heat, and wherein the localized region of the rotor disk varies among the plurality of rotor disks;
(b) installing the first rotor disk;
(c) repeating steps (a) and (b) for each rotor disk of the plurality of rotor disks to form a stacked rotor assembly; and
allowing the stacked rotor assembly to cool, wherein the respective connecting element of each rotor disk that has been selectively deflected contracts into an interference fit with an adjacent rotor disk, wherein the rotor disk defines a central rotor bore and the connecting element is disposed radially outboard of the central rotor bore; wherein the localized region is adjacent the central rotor bore; and wherein the method further comprises forming the inductive heating fixture for installation within the central rotor bore.

2. The method of claim 1 , wherein the localized region of the rotor disk varies among the plurality of rotor disks.

3. The method of claim 2 , wherein the applying heat to a localized region is accomplished at a ramp rate and a soak time.

4. The method of claim 3 , wherein the soak time is between 30 minutes and 90 minutes for the respective rotor disk.

5. The method of claim 2 , further comprising, prior to step (a), determining a location of the localized region of a respective rotor disk including the connecting element, one or more areas of the geometry suitable for attachment of the inductive heating fixture, and an amount of thermal deflection needed in the connecting element.

6. The method of claim 2 , wherein the rotor disk comprises a first contact surface, a second contact surface opposite the first contact surface, and the connecting element extending from the first contact surface; wherein the applying heat to the localized region is accomplished by positioning the inductive heating fixture adjacent the second contact surface at a radial location opposite the connecting element.

7. The method of claim 2 , wherein the connecting element of the rotor disk projects outwardly from an upstream surface of the rotor disk; and wherein the applying heat to the localized region is accomplished by positioning the inductive heating fixture adjacent the connecting element.

8. The method of claim 2 , wherein the connecting element of the rotor disk is disposed at an interface between adjacent surfaces of the rotor disk; and wherein the applying heat to the localized region is accomplished by positioning the inductive heating fixture at a location distal to the interface.

9. The method of claim 2 , wherein the connecting element of the rotor disk comprises the first connecting element and a second connecting element; and wherein the applying heat to the localized region is accomplished by positioning a first inductive heating fixture proximate to the first connecting element and a second inductive heating fixture to a surface opposite the second connecting element.

10. The method of claim 1 , wherein the allowing the stacked rotor assembly to cool is accomplished over a cool-down time of between 6 hours and 8 hours, the cool-down time being calculated between when a last rotor disk is installed and when the localized regions of the respective disks reach an ambient temperature.

11. A gas turbine having a rotor assembly comprising a plurality of rotor disks interconnected to form a stacked rotor shaft, assembled according to the method of claim 1 .

Assignees

• Gen Electric

Inventors

• Friedman Michael Ericson
• Syed Minhajuddin
• Michaud William Michael
• Lum Lamont Joseph

Classifications

• F04D29/644 Primary

  especially adapted for elastic fluid pumps · CPC title

• F04D29/053

  Shafts · CPC title

• F04D19/02

  Multi-stage pumps · CPC title

• H05B6/102

  the metal pieces being rotated while induction heated · CPC title

• F01D25/285

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title